A profiled blade for a fan impeller comprising a profiled body produced from at least one bent sheet metal strip. The profiled body includes a profile top part with a convex curvature, a profile bottom part located at a distance from the profile top part, and first and second profile noses. Each of the profile noses has a convex curvature and joins the profile top part to the profile bottom part at ends of the profiled body. The profile top part and/or the profile bottom part is divided into at least first and second profile sections. The first profile section is joined to the first profile nose and the second profile section is joined to the second profile nose. A first free end region of the first profile section is joined to a second free end region of the second profile section by adhesive force.

A rotary machine includes a machine stator and a machine rotor rotatable relative to the machine stator and having a metal shaft portion, a composite impeller portion, and at least a first metal ring portion securing the composite impeller portion to the metal shaft portion, the metal ring portion having a first interface with the composite impeller portion and a second interface with the metal shaft portion.

Cover plate connections for a hollow fan blade are disclosed. An example fan blade includes a hollow body including a surface defining an airfoil, the hollow body including an aperture extending through the surface, a cover plate, and at least one connection element to couple the cover plate to the surface such that the cover plate encloses the aperture.

A method for assembling a set including an inner wall, a shrouded outer wall and an intermediate element, each presenting substantially circular sections, the shrouded outer wall presenting a shape substantially complementary to a shape of outer and inner surfaces of the intermediate element, and whose inner surface covers the outer surface of the intermediate element. In particular, the method includes a step of placing a brazing sheet, whose melting temperature is lower than melting temperatures of other elements of the set, over an assembly surface in contact with another assembly surface, and a step of heating, by a furnace, a set including the outer or inner walls and the intermediate element between which is interposed a brazing sheet so as to fix the outer or inner wall by brazing on the intermediate element.

A manufacturing process is provided during which a thrust reverser cascade is formed for an aircraft propulsion system. During the formation of the thrust reverser cascade, a first panel of material is stamped into a first corrugated body. A second panel of material is stamped into a second corrugated body. The first corrugated body is bonded to the second corrugated body.

A compressor that includes an impeller, a diffuser and a shroud. The diffuser includes vanes and one or more projections, each of which extends from a top of a vane. The shroud includes one or more holes. The shroud covers the impeller and the diffuser such that each projection protrudes through one of the holes. The shroud is then secured to the projections by an adhesive.

A method for attaching an abradable piece support by crimping to the radially inner wall of a vane sector of a turbomachine, comprises deforming opposite rims of the radially inner wall on opposite free axial ends of the abradable piece support respectively, jointly, by means of two pressure blocks (40A, 40B) respectively, which are attached to each other and delimiting a space (42) between them intended to accommodate a median portion of the abradable piece support. A crimping attachment device (30) comprising such pressure blocks can in particular be operated by means of a conventional press, and can enable the method for attaching the abradable piece support to be automated.

A hybrid metal and composite spool includes metal rings on an outer diameter of a composite spool shell. Metal rings may include features such as annular or axial dovetail slots. Adhesive layers may be between the metal rings and composite shell which may be connected by a shrink bonded joint. The metal rings may include a single seal tooth ring with an annular radially extending seal tooth. A method for fabricating the spool may include fabricating one or more metal rings with the features therein, positioning the metal rings in place on an outer surface of an uncured composite spool shell of the spool before curing the shell, and curing the shell with the one or more metal rings positioned in place. Alternatively, rings may be heated to a temperature at least sufficient to slide rings over a cured composite shell, and allowed to cool and shrink onto shell.

A method for manufacturing a turbine assembly having at least one aerofoil unit including at least a basically hollow aerofoil with at least one cooling passage for a cooling medium and at least one entry surface, wherein the at least one cooling passage enters at the at least one entry surface, and further the turbine assembly has at least one cover plate that at least partially covers the at least one entry surface. In order to provide a reliable attachment the method includes the step of attaching the at least one cover plate with one single, continuous, connecting structure to the at least one aerofoil unit.

The invention relates to a shaft-hub connection (1), particularly for mounting a rotor wheel on a shaft (10). The shaft-hub connection (1) comprises a shaft (10), a hub (20) and a filler material (30). The shaft (10) comprises an end section (11) on one end. A receiving region (21) is arranged in the hub (20). The end section (11) is arranged in the receiving region (21), with an intermediate layer of the filler material (30) positioned inbetween. The filler material (30) forms undercuts in the axial and rotational direction, in relation to the end section (11) and in relation to the receiving region (21), so as to create a positive embodiment of the shaft-hub connnection (1).